GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 100,000 Max Cl/Cd: 54.43 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe670-il-100000-n5.txt Download as CSV file: xf-goe670-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3084 0.10518 0.10028 -0.0360 1.0000 0.0728
-9.750 -0.3230 0.10270 0.09786 -0.0372 1.0000 0.0737
-9.250 -0.3931 0.10063 0.09544 -0.0364 1.0000 0.0598
-9.000 -0.3921 0.09759 0.09243 -0.0355 1.0000 0.0578
-8.750 -0.3978 0.09449 0.08938 -0.0350 1.0000 0.0559
-8.250 -0.4647 0.08579 0.08093 -0.0369 1.0000 0.0497
-8.000 -0.4722 0.08290 0.07808 -0.0358 1.0000 0.0495
-7.750 -0.4809 0.07964 0.07485 -0.0352 1.0000 0.0494
-7.500 -0.4910 0.07554 0.07074 -0.0357 1.0000 0.0496
-7.000 -0.4867 0.07165 0.06688 -0.0329 0.9993 0.0520
-6.750 -0.4641 0.06750 0.06263 -0.0377 0.9942 0.0533
-6.500 -0.4452 0.06059 0.05549 -0.0445 0.9878 0.0529
-6.250 -0.4263 0.05421 0.04880 -0.0495 0.9822 0.0527
-6.000 -0.4054 0.04902 0.04330 -0.0528 0.9772 0.0531
-5.750 -0.3833 0.04566 0.03968 -0.0547 0.9724 0.0549
-5.500 -0.3604 0.04150 0.03513 -0.0567 0.9675 0.0566
-5.250 -0.3375 0.03721 0.03035 -0.0581 0.9628 0.0569
-5.000 -0.3146 0.03365 0.02626 -0.0587 0.9577 0.0576
-4.750 -0.2862 0.03057 0.02261 -0.0598 0.9543 0.0587
-4.500 -0.2633 0.02836 0.01988 -0.0594 0.9488 0.0599
-4.250 -0.2342 0.02668 0.01778 -0.0600 0.9447 0.0623
-4.000 -0.2017 0.02581 0.01682 -0.0613 0.9414 0.0645
-3.750 -0.1774 0.02487 0.01570 -0.0608 0.9349 0.0662
-3.500 -0.1450 0.02378 0.01438 -0.0618 0.9311 0.0684
-3.250 -0.1139 0.02280 0.01318 -0.0624 0.9270 0.0710
-3.000 -0.0872 0.02198 0.01214 -0.0621 0.9210 0.0738
-2.750 -0.0538 0.02133 0.01150 -0.0633 0.9171 0.0773
-2.500 -0.0248 0.02096 0.01110 -0.0635 0.9114 0.0832
-2.250 0.0045 0.02045 0.01053 -0.0638 0.9054 0.0898
-2.000 0.0394 0.01993 0.01001 -0.0651 0.9018 0.0974
-1.750 0.0649 0.01953 0.00960 -0.0646 0.8948 0.1057
-1.500 0.0964 0.01920 0.00923 -0.0653 0.8893 0.1180
-1.250 0.1325 0.01871 0.00881 -0.0668 0.8859 0.1314
-1.000 0.1554 0.01844 0.00861 -0.0659 0.8772 0.1444
-0.750 0.1892 0.01806 0.00829 -0.0669 0.8725 0.1600
-0.500 0.2213 0.01772 0.00805 -0.0677 0.8672 0.1798
-0.250 0.2486 0.01743 0.00791 -0.0675 0.8592 0.2069
0.000 0.2857 0.01687 0.00766 -0.0693 0.8552 0.2845
0.500 0.4199 0.01467 0.00722 -0.0841 0.8427 1.0000
0.750 0.4487 0.01443 0.00686 -0.0837 0.8280 1.0000
1.000 0.4764 0.01423 0.00656 -0.0830 0.8126 1.0000
1.250 0.5035 0.01407 0.00631 -0.0823 0.7963 1.0000
1.500 0.5298 0.01397 0.00614 -0.0815 0.7803 1.0000
1.750 0.5554 0.01394 0.00604 -0.0807 0.7652 1.0000
2.000 0.5810 0.01393 0.00598 -0.0799 0.7504 1.0000
2.250 0.6070 0.01391 0.00592 -0.0792 0.7344 1.0000
2.500 0.6338 0.01390 0.00585 -0.0786 0.7174 1.0000
2.750 0.6593 0.01394 0.00583 -0.0778 0.6994 1.0000
3.000 0.6859 0.01398 0.00582 -0.0771 0.6805 1.0000
3.250 0.7128 0.01406 0.00581 -0.0765 0.6602 1.0000
3.500 0.7385 0.01419 0.00585 -0.0757 0.6389 1.0000
3.750 0.7622 0.01439 0.00598 -0.0746 0.6163 1.0000
4.000 0.7851 0.01462 0.00614 -0.0734 0.5928 1.0000
4.250 0.8055 0.01488 0.00637 -0.0717 0.5650 1.0000
4.500 0.8246 0.01515 0.00659 -0.0698 0.5296 1.0000
4.750 0.8426 0.01550 0.00679 -0.0676 0.4829 1.0000
5.000 0.8589 0.01598 0.00700 -0.0652 0.4362 1.0000
5.250 0.8752 0.01656 0.00734 -0.0630 0.3985 1.0000
5.500 0.8923 0.01714 0.00777 -0.0610 0.3686 1.0000
5.750 0.9099 0.01773 0.00824 -0.0591 0.3441 1.0000
6.000 0.9283 0.01828 0.00872 -0.0574 0.3249 1.0000
6.250 0.9471 0.01883 0.00922 -0.0558 0.3090 1.0000
6.500 0.9665 0.01936 0.00974 -0.0543 0.2962 1.0000
6.750 0.9859 0.01992 0.01029 -0.0529 0.2852 1.0000
7.000 1.0059 0.02045 0.01086 -0.0516 0.2750 1.0000
7.250 1.0260 0.02099 0.01145 -0.0502 0.2651 1.0000
7.500 1.0442 0.02157 0.01203 -0.0487 0.2530 1.0000
7.750 1.0604 0.02212 0.01260 -0.0468 0.2374 1.0000
8.000 1.0756 0.02265 0.01318 -0.0448 0.2201 1.0000
8.250 1.0908 0.02318 0.01377 -0.0428 0.2030 1.0000
8.500 1.1060 0.02370 0.01436 -0.0408 0.1862 1.0000
8.750 1.1191 0.02425 0.01494 -0.0385 0.1637 1.0000
9.000 1.1316 0.02493 0.01558 -0.0362 0.1274 1.0000
9.250 1.1360 0.02636 0.01659 -0.0331 0.0847 1.0000
9.500 1.1423 0.02790 0.01802 -0.0303 0.0577 1.0000
9.750 1.1491 0.02938 0.01942 -0.0276 0.0464 1.0000
10.000 1.1542 0.03091 0.02092 -0.0248 0.0413 1.0000
10.250 1.1604 0.03230 0.02246 -0.0222 0.0377 1.0000
10.500 1.1638 0.03389 0.02415 -0.0195 0.0349 1.0000
10.750 1.1630 0.03578 0.02613 -0.0167 0.0332 1.0000
11.000 1.1651 0.03751 0.02802 -0.0143 0.0320 1.0000
11.250 1.1666 0.03937 0.03005 -0.0120 0.0308 1.0000
11.500 1.1676 0.04134 0.03218 -0.0100 0.0296 1.0000
11.750 1.1677 0.04348 0.03448 -0.0082 0.0286 1.0000
12.000 1.1670 0.04577 0.03688 -0.0066 0.0274 1.0000
12.250 1.1654 0.04828 0.03947 -0.0053 0.0265 1.0000
12.500 1.1630 0.05106 0.04231 -0.0040 0.0256 1.0000
12.750 1.1656 0.05349 0.04488 -0.0030 0.0251 1.0000
13.000 1.1683 0.05605 0.04762 -0.0021 0.0244 1.0000
13.250 1.1709 0.05870 0.05046 -0.0014 0.0240 1.0000
13.500 1.1726 0.06156 0.05349 -0.0009 0.0235 1.0000
13.750 1.1724 0.06468 0.05681 -0.0006 0.0231 1.0000
14.000 1.1693 0.06818 0.06051 -0.0006 0.0224 1.0000
14.250 1.1656 0.07184 0.06437 -0.0010 0.0220 1.0000
14.500 1.1594 0.07595 0.06867 -0.0017 0.0216 1.0000
14.750 1.1519 0.08036 0.07331 -0.0029 0.0213 1.0000
15.000 1.1430 0.08511 0.07825 -0.0045 0.0210 1.0000
15.250 1.1327 0.09035 0.08368 -0.0066 0.0208 1.0000
15.500 1.1214 0.09599 0.08949 -0.0092 0.0205 1.0000
15.750 1.1086 0.10218 0.09587 -0.0123 0.0203 1.0000
16.000 1.0937 0.10915 0.10303 -0.0161 0.0203 1.0000
16.250 1.0763 0.11715 0.11126 -0.0209 0.0204 1.0000
16.500 1.0552 0.12651 0.12079 -0.0267 0.0205 1.0000
16.750 1.0245 0.13925 0.13378 -0.0348 0.0212 1.0000
17.000 0.9705 0.16084 0.15558 -0.0479 0.0229 1.0000
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